论文部分内容阅读
建立了欧拉－拉格朗日坐标系下液体火箭发动机内部工作过程二维轴对称两相湍流化学反应流的完全Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ模型。应用该模型对气氢液氧同轴式单喷嘴燃烧室热态流场进行了数值模拟，得到了全流场的速度矢量分布、燃气组分等值线、流场等温线、流场等压线和流场等马赫线。计算是在任意斜交曲线坐标系下进行的，采用等参数正变换（代数变换）把物理平面上不规则计算域变换成了计算平面上的矩形域，控制方程也进行了相应的变换。计算结果表明，用计算流体力学（ＣＦＤ）的方法研究和分析液体火箭发动机内部工作过程是可行的。
A complete Navier-Stokes model of two-dimensional axisymmetric two-phase turbulent chemical reaction flow in a liquid rocket engine operating in the Eulerian-Lagrangian coordinate system is established. The model was used to simulate the thermal flow field in a single nozzle combustor with gas-liquid oxygen and oxygen. The velocity vector distribution, gas composition isotherm, flow field isotherm, Mach lines such as lines and flow. The calculation is carried out under any skew curve coordinate system. The isoparametric positive transformation (algebraic transformation) is used to transform the irregular computational domain on the physical plane into the rectangular domain on the computational plane, and the governing equation is also transformed accordingly. The calculation results show that it is feasible to study and analyze the internal working process of liquid rocket engine by the method of computational fluid dynamics (CFD).